UNT Libraries Government Documents Department - 130 Matching Results

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Aerodynamic Characteristics at Mach Numbers From 2.5 to 3.5 of a Canard Bomber Configuration Designed for Supersonic Cruise Flight

Description: Report presenting an investigation of a canard-type configuration designed for supersonic cruise flight in the Unitary Plan wind tunnel. Tests were conducted over a range of angles of attack and angles of sideslip. Results regarding the effect of forebody configuration, effects of Reynolds number and transition, effect of canard and elevon deflection, and effect of vertical surfaces are provided.
Date: September 10, 1958
Creator: Carmel, Melvin M.; Kelly, Thomas C. & Gregory, Donald T.
Item Type: Refine your search to only Report
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Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18

Description: Memorandum presenting a study of aerodynamic performance and static stability and control at hypersonic speeds. In the first part of the study, the effect of interference lift is investigated by tests of asymmetric models with conical fuselages and arrow plan-form wings. In the second part, the aerodynamic performance and static stability and control characteristics of a hypersonic glider are investigated in somewhat greater detail.
Date: September 17, 1958
Creator: Syvertson, Clarence A.; Gloria, Hermilo R. & Sarabia, Michael F.
Item Type: Refine your search to only Report
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Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination

Description: From Introduction: "Wind-tunnel and flight tests have shown that conical leading-edge camber on a thin low-aspect-ratio delta wing results in increasing the lift-drag ratio at transonic and low supersonic speeds (refs. 1 and 2). References 3 and 4 present the results of two previous investigations of this general program. A more detailed analysis of the pressure distributions of reference 5 is presented herein in terms of total section loads and overall wing-body characteristics."
Date: September 26, 1958
Creator: Mugler, John P., Jr.
Item Type: Refine your search to only Report
open access

An Analysis of Ramjet Engines Using Supersonic Combustion

Description: From Introduction: "The concept of supersonic combustion is by no means new, although little work appears to have been published on the subject. For example, an analysis of supersonic combustion to provide lift under a wing is given in reference 1. Reference 2 discusses applications to hypersonic ramjets being studied at the University of Michigan."
Date: September 1958
Creator: Weber, Richard J. & MacKay, John S.
Item Type: Refine your search to only Report
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Analysis of the Creep Behavior of a Square Plate Loaded in Edge Compression

Description: From Introduction: "In reference 1 results of creep tests and empirical method for predicting collapse times are presented for plates loaded in compression on two opposite edges and with the remaining edges unloaded and supported in V-groove fixtures. Other approximate methods for handling plates having types of edge support are suggested in reference 2; however, experimental verification for these methods is quite limited. In reference 3 an analysis based on small-deflection theory is made of … more
Date: September 1958
Creator: McComb, Harvey G., Jr.
Item Type: Refine your search to only Report
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Analysis of Turbulent Flow and Heat Transfer in Noncircular Passages

Description: From Introduction: "In reference 1, wall temperature distributions for turbulent flow in rectangular and triangular ducts were calculated by using experimental velocity distributions and average heat-transfer coefficients, together with assumed similarity of the wall heat-transfer and wall shear-stress variations; no attempt was made to calculate either the heat-transfer coefficients or the velocity and temperature distributions in the fluid field. Some calculations of velocity and shear-stress… more
Date: September 1958
Creator: Deissler, Robert G. & Taylor, Maynard F.
Item Type: Refine your search to only Report
open access

Analytical and Experimental Investigation of Temperature Recovery Factors for Fully Developed Flow of Air in a Tube

Description: Note presenting an analysis made for predicting temperature recovery factors for fully developed flow in a tube. Most of the attention was confined to turbulent flow. Both analytical and experimental results are provided for the air flow.
Date: September 1958
Creator: Deissler, R. G.; Weiland, W. F. & Lowdermilk, W. H.
Item Type: Refine your search to only Report
open access

Application of the Method of Coordinate Perturbation to Unsteady Duct Flow

Description: The method of coordinate perturbation is applied to the unsteady flow of a compressible fluid in ducts of variable cross section. Solutions, in the form of perturbation series, are obtained for unsteady flows in ducts for which the logarithmic derivative of area variation with respect to the space coordinate is a function of the 'smallness' parameter of the perturbation series. This technique is applied to the problem of the interaction of a disturbance and a shock wave in a diffuser flow. It i… more
Date: September 1958
Creator: Himmel, Seymour C.
Item Type: Refine your search to only Report
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An Approach to the Problem of Estimating Severe and Repeated Gust Loads for Missile Operations

Description: Note presenting an analysis of available airplane measurements of vertical gust velocity in order to arrive at a simple description of the frequency and intensity of gust velocities experienced by airplanes in operations. For the purpose of application to missile operations, the results obtained are modified to eliminate the effects of storm-avoidance procedures normally followed in airplane operations.
Date: September 1958
Creator: Press, Harry & Steiner, Roy
Item Type: Refine your search to only Report
open access

Approximate method for calculating motions in angles of attack and sideslip due to step pitching- and yawing-moment inputs during steady roll

Description: Report presenting an extension of a method for calculating motions in angles of attack and sideslip resulting from a trim angle of attack and steady rolling velocity to the condition of pitching- and yawing-moment inputs. The resulting formulas are intended primarily for rolling-velocity conditions in which rolling divergence is not encountered.
Date: September 1958
Creator: Moul, Martin T. & Brennan, Teresa R.
Item Type: Refine your search to only Report
open access

Approximate Method for Calculation of Laminar Boundary Layer With Heat Transfer on a Cone at Large Angle of Attack in Supersonic Flow

Description: Note presenting the use of an integral technique to reduce the laminar boundary-layer equations on the windward generator of the plane of symmetry to a set of simultaneous algebraic equations. The method enables the skin friction coefficients and Stanton number to be calculated in a much shorter time than was needed to obtain exact numerical solutions from the boundary-layer equations.
Date: September 1958
Creator: Brunk, William E.
Item Type: Refine your search to only Report
open access

Approximate solutions of a class of similarity equations for three-dimensional, laminar, incompressible boundary-layer flows

Description: Report presenting an analysis for obtaining approximate solutions of the similarity equations for three-dimensional laminar-boundary-layer flows over a flat surface under main-flow streamlines that are translates and representable as infinite series expansions.
Date: September 1958
Creator: Hansen, Arthur G. & Herzig, Howard Z.
Item Type: Refine your search to only Report
open access

Combustor performance with various hydrogen-oxygen injection methods in a 200-pound-thrust rocket engine

Description: Report presenting a determination of the characteristics velocity of liquid oxygen and gaseous hydrogen as a function of mixture ratio in a nominal 200-pound-thrust variable-length rocket engine. Fourteen injectors, which varied mixing and oxygen atomization, were investigated. The four types of injector designs included triplets of two hydrogen jets impinging on one oxygen jet, concentric injection with hydrogen surrounding a jet of oxygen, radial injection of oxygen with variations in hydroge… more
Date: September 30, 1958
Creator: Heidmann, M. F. & Baker, Louis, Jr.
Item Type: Refine your search to only Report
open access

Comparison of Calculated and Experimental Temperatures and Coolant Pressure Losses for a Cascade of Small Air-Cooled Turbine Rotor Blades

Description: From Summary: "Average spanwise blade temperatures and cooling-air pressure losses through a small (1.4-in, span, 0.7-in, chord) air-cooled turbine blade were calculated and are compared with experimental nonrotating cascade data. Two methods of calculating the blade spanwise metal temperature distributions are presented. The method which considered the effect of the length-to-diameter ratio of the coolant passage on the blade-to-coolant heat-transfer coefficient and assumed constant coolant pr… more
Date: September 4, 1958
Creator: Stepka, Francis S.
Item Type: Refine your search to only Report
open access

Comparison of Injectors With a 200-Pound-Thrust Ammonia-Oxygen Engine

Description: "Characteristic exhaust velocity was measured for a small range of mixture ratios with four different injectors. Performances of parallel-sheet, like-on-like, and triplet injectors were about the same, but a parallel-jet injector had a much lower performance. Performance values for ammonia-oxygen were slightly lower than for heptane-oxygen" (p. 1).
Date: September 4, 1958
Creator: Priem, Richard J. & Clark, Bruce J.
Item Type: Refine your search to only Report
open access

Comparison of shock-expansion theory with experiment for the lift, drag, and pitching-moment characteristics of two wing-body combinations at M=5.0

Description: Report presenting lift, drag, and pitching-moment coefficients for two wing-body combinations as determined from tests at Mach number 5.0 and angles of attack up to 9 degrees. The test models consisted of small thin wings mounted on a body composed of a fineness-ratio-3 ogival nose and a fineness-ratio-2 cylindrical afterbody.
Date: September 1958
Creator: Savin, Raymond C.
Item Type: Refine your search to only Report
open access

Cumulative Fatigue Damage at Elevated Temperature

Description: "A study of cumulative fatigue damage at elevated temperatures was conducted using heat-treated SAE 4130 alloy steel. The S-N curves at room temperature, 400 degrees Fahrenheit, and 800 degrees Fahrenheit were obtained from rotating-beam fatigue tests. Two-step, three-step, and five-step cumulative-damage fatigue tests were conducted on rotating-beam fatigue specimens at room temperature, 400 degrees Fahrenheit, and 800 degrees Fahrenheit. The results of the cumulative-damage tests are compared… more
Date: September 1958
Creator: Rey, William K.
Item Type: Refine your search to only Report
open access

Design and Experimental Investigation of a Single-Stage Turbine With a Rotor Entering Relative Mach Number of 2

Description: Memorandum presenting a design and experimental investigation of a single-stage supersonic turbine. The turbine was designed for a rotor entering relative Mach number of 2. Results regarding the overall turbine performance, outer-wall static-pressure variation, momentum-loss considerations, effect of rotor modifications, and supersonic starting are provided.
Date: September 15, 1958
Creator: Moffitt, Thomas P.
Item Type: Refine your search to only Report
open access

Design and Experimental Performance of a 0.35 Hub-Tip Radius Ratio Transonic Axial-Flow-Compressor Rotor Designed for 40 Pounds Per Second Per Unit Frontal Area

Description: Memorandum presenting an investigation to determine the feasibility of a high-performance transonic axial-flow compressor stage with a weight flow of 40 pounds per second per square foot of frontal area. A transonic axial-flow inlet stage with a hub-tip ratio of 0.35 and an axial Mach number of approximately 0.75 was designed and fabricated. Results regarding overall rotor performance, flow parameters, radial matching of blade-element sections, and comparison of blade-element parameters with de… more
Date: September 4, 1958
Creator: Montgomery, John C. & Yasaki, Paul T.
Item Type: Refine your search to only Report
open access

Effect of Advance Ratio on Flight Performance of a Modified Supersonic Propeller

Description: Note presenting results of a flight investigation to determine the aerodynamic characteristics of a supersonic propeller modified by the incorporation of higher than optimum advance angles. The propeller was designed for a forward Mach number of 0.95, an advance ratio of 3.2, and a power coefficient of 0.42. The efficiency of the propeller is approximately 79 percent at a Mach number of 0.95.
Date: September 1958
Creator: Hammack, Jerome B. & O'Bryan, Thomas C.
Item Type: Refine your search to only Report
open access

The Effect of Free-Stream Turbulence on Heat Transfer From a Flat Plate

Description: Turbulence was generated by using screens, and the turbulence percentage was measured by a hot-wire anemometer both in the boundary layer and the free stream. The local heat-transfer coefficient was measured at 12 locations along the plate for the cases of various turbulence levels. The transition Reynolds number from laminar to turbulent flow decreases as the main-stream turbulence level increases. In the range of laminar heat transfer the effect of turbulence in the main flow was not great, b… more
Date: September 1958
Creator: Sugawara, Sugao; Sato, Takashi; Komatsu, Hiroyasu & Osaka, Hiroichi
Item Type: Refine your search to only Report
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